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    ASYMMETRIC FAN NOZZLE IN HIGH-BPR SEPARATE-FLOW NACELLE
    1.
    发明申请
    ASYMMETRIC FAN NOZZLE IN HIGH-BPR SEPARATE-FLOW NACELLE 审中-公开
    不对称风扇喷嘴在高BPR单独流动的NACELLE

    公开(公告)号：WO2014143281A8

    公开(公告)日：2014-11-27

    申请号：PCT/US2013075955

    申请日：2013-12-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORD WESLEY K ,  MALECKI ROBERT E

    IPC: F02K1/30 ,  F02C7/00 ,  F02K1/28

    CPC classification number: F02K3/06 ,  B64D33/04 ,  B64D2033/0286 ,  F01D25/24 ,  F02C3/04 ,  F02K1/78 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2250/73

    Abstract: A fan nozzle for an aircraft gas turbine engine is comprised of a core engine cowl that is disposed within a fan cowl so that an air flow area is defined there between. The core engine cowl and fan cowl are disposed around a horizontal central plane. The fan cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a first radius and a lower substantially semi-circular portion having a second radius. The core engine cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a third radius and a lower substantially semi-circular portion having a third radius. The upper substantially semi-circular portion of the core engine cowl includes a left arcuate member and a right arcuate member. The second radius is less than the first radius and the third radius is less than the fourth radius.

    Abstract translation: 用于飞机燃气涡轮发动机的风扇喷嘴由设置在风扇罩内的核心发动机罩组成，从而在其间限定空气流动区域。 核心发动机罩和风扇罩布置在水平中心平面周围。 风扇罩具有大致圆形形状，并且由具有第一半径的上部基本上半圆形部分和具有第二半径的下部基本上半圆形部分形成。 芯发动机整流罩具有大致圆形形状，并且由具有第三半径的上部大致半圆形部分和具有第三半径的下部基本上半圆形部分形成。 核心发动机罩的上部基本上半圆形的部分包括左弓形件和右弓形件。 第二半径小于第一半径，第三半径小于第四半径。

    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO
    2.
    发明专利
    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO 未知

    公开(公告)号：CA2898207C

    公开(公告)日：2020-03-10

    申请号：CA2898207

    申请日：2014-02-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  MALECKI ROBERT E

    IPC: F02K3/068 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06

    Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.

    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO
    3.
    发明专利
    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO 未知

    公开(公告)号：CA2898207A1

    公开(公告)日：2014-08-14

    申请号：CA2898207

    申请日：2014-02-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  MALECKI ROBERT E

    IPC: F02K3/068

    Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.

    BYPASS DUCT HEAT EXCHANGER PLACEMENT
    5.
    发明公开
    BYPASS DUCT HEAT EXCHANGER PLACEMENT 审中-公开
    BYPASSKANAL-WÄRMETAUSCHERPLATZIERUNG

    公开(公告)号：EP3049641A4

    公开(公告)日：2017-06-28

    申请号：EP14849975

    申请日：2014-07-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MALECKI ROBERT E

    IPC: F01D25/12 ,  F02C7/057 ,  F02C7/12 ,  F02C7/14 ,  F02C7/18 ,  F02K3/115

    CPC classification number: F02K3/115 ,  F02C7/14 ,  F02C7/185 ,  F05D2250/52 ,  F05D2260/213

    Abstract: A bypass duct for a gas turbine engine includes as an inner surface, an intermediate case, an inner fixed structure (IFS), and a heat exchanger outlet mounted to the outer surface of the intermediate case or the forward portion of the IFS. The heat exchanger outlet is oriented to bathe the surface of the bypass duct case downstream of the heat exchanger outlet with low momentum heat exchanger exhaust to reduce skin friction losses for the bypass duct.

    Abstract translation: 用于燃气涡轮发动机的旁路管道包括作为内表面，中间壳体，内部固定结构（IFS）以及安装到中间壳体的外表面或IFS的前部的热交换器出口。 热交换器出口被定向为用低动量热交换器排气使热交换器出口下游的旁路管壳体的表面沐浴以减少旁路管道的表皮摩擦损失。

    ASYMMETRIC FAN NOZZLE IN HIGH-BPR SEPARATE-FLOW NACELLE
    6.
    发明公开
    ASYMMETRIC FAN NOZZLE IN HIGH-BPR SEPARATE-FLOW NACELLE 有权
    EANER GONDEL MIT HOHEMNEBENSTROMVERHÄLTNISUNDERNTEM DURCHFLUSS的不同寻常者

    公开(公告)号：EP2971727A4

    公开(公告)日：2016-11-16

    申请号：EP13878444

    申请日：2013-12-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORD WESLEY K ,  MALECKI ROBERT E

    IPC: F02K1/30 ,  B64D33/04 ,  F02C7/00 ,  F02K1/28

    CPC classification number: F02K3/06 ,  B64D33/04 ,  B64D2033/0286 ,  F01D25/24 ,  F02C3/04 ,  F02K1/78 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2250/73

    Abstract: A fan nozzle for an aircraft gas turbine engine is comprised of a core engine cowl that is disposed within a fan cowl so that an air flow area is defined therebetween. The core engine cowl and fan cowl are disposed around a horizontal central plane. The fan cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a first radius and a lower substantially semi-circular portion having a second radius. The core engine cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a third radius and a lower substantially semi-circular portion having a third radius. The upper substantially semi-circular portion of the core engine cowl includes a left arcuate member and a right arcuate member. The second radius is less than the first radius and the third radius is less than the fourth radius.

    Abstract translation: 用于飞机燃气涡轮发动机的风扇喷嘴由设置在风扇整流罩内的核心发动机罩组成，从而在其间限定空气流动区域。 核心发动机罩和风扇罩布置在水平中心平面周围。 风扇整流罩具有大致圆形的形状，并且由具有第一半径的上部大致半圆形部分和具有第二半径的下部基本上半圆形部分形成。 核心发动机罩具有大致圆形形状，并且由具有第三半径的上部大致半圆形部分和具有第三半径的下部基本上半圆形部分形成。 核心发动机罩的上部大致半圆形的部分包括一个左弧形部件和一个右弧形部件。 第二半径小于第一半径，第三半径小于第四半径。

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    9.
    发明公开
    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
    与小的压力比的风扇马达和之间的入口和风扇尺寸的尺寸关系

    公开(公告)号：EP3052789A4

    公开(公告)日：2016-11-09

    申请号：EP14850031

    申请日：2014-09-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORD WESLEY K ,  MALECKI ROBERT E ,  QIU YUAN ,  ROSE BECKY E ,  GILSON JONATHAN

    IPC: F02C7/36 ,  F02C7/04 ,  F02K3/068

    CPC classification number: F02K3/068 ,  F01D25/24 ,  F02C7/04 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671

    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.

    Abstract translation: 。根据实施例的示例，一种燃气涡轮发动机组件包括，除其他事项外，风扇确实具有风扇叶片的复数。 风扇的直径具有尺寸D做是基于所述风扇叶片的尺寸。 每个风扇叶片具有领先优势。 的入口部分向前风扇位于。 入口部分的长度具有至少一些风扇叶片的和在入口部分的前边缘的前缘的位置之间的尺寸L。 L的尺寸关系/ D是约0.2至约12:45之间。

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